Injector Coupled High Frequency Instability in Liquid Rocket Engines PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Injector Coupled High Frequency Instability in Liquid Rocket Engines PDF full book. Access full book title Injector Coupled High Frequency Instability in Liquid Rocket Engines by Timothy D. Hinerman. Download full books in PDF and EPUB format.
Author: Timothy D. Hinerman
Publisher:
ISBN:
Category : Liquid propellant rockets
Languages : en
Pages : 116
Get Book Here
Book Description
Author: Timothy D. Hinerman
Publisher:
ISBN:
Category : Liquid propellant rockets
Languages : en
Pages : 116
Get Book Here
Book Description
Author: Mark L. Dranovsky
Publisher: AIAA (American Institute of Aeronautics & Astronautics)
ISBN: 9781563479212
Category : Technology & Engineering
Languages : en
Pages : 352
Get Book Here
Book Description
This is the first book in the literature to cover the development and testing practices for liquid rocket engines in Russia and the former Soviet Union.Combustion instability represents one of the most challenging probelms in the development of propulsion engines. A famous example is the F-1 engines for the first stage of the Saturn V launch vehicles in the Apollo project. More than 2000 full engine tests and a vast number of design modifications were conducted to cure the instability problem.This book contains first-hand information about the testing and development practices for treating liquid rocket combustion-instability problems in Russia and the former Soviet Union. It covers more than 50 years of research, with an emphasis placed on the advances made since 1970.The book was prepared by a former R&D director of the Research Institute of Chemical Engineering, NIICHIMMASH, the largest liquid rocket testing center in the world, and has been carefully edited by three well-known experts in the field.
Author: Vigor Young
Publisher: AIAA
ISBN: 9781600864186
Category : Liquid propellant rockets
Languages : en
Pages : 606
Get Book Here
Book Description
Annotation Since the invention of the V-2 rocket during World War II, combustion instabilities have been recognized as one of the most difficult problems in the development of liquid propellant rocket engines. This book is the first published in the United States on the subject since NASA's Liquid Rocket Combustion Instability (NASA SP-194) in 1972. In this book, experts cover four major subject areas: engine phenomenology and case studies, fundamental mechanisms of combustion instability, combustion instability analysis, and engine and component testing. Especially noteworthy is the inclusion of technical information from Russia and China--a first.
Author: David T. Harrje
Publisher:
ISBN:
Category : Liquid propellant rockets
Languages : en
Pages : 674
Get Book Here
Book Description
The solution of problems of combustion instability for more effective communication between the various workers in this field is considered. The extent of combustion instability problems in liquid propellant rocket engines and recommendations for their solution are discussed. The most significant developments, both theoretical and experimental, are presented, with emphasis on fundamental principles and relationships between alternative approaches.
Author: Justin S. Hardi
Publisher:
ISBN:
Category : Liquid propellant rockets
Languages : en
Pages : 207
Get Book Here
Book Description
Self-sustaining pressure oscillations in the combustion chamber, or combustion instability, is a commonly encountered and potentially damaging phenomenon in liquid propellant rocket engines (LPREs). In the high-frequency variety of combustion instability, the pressure oscillations in the combustion chamber take on the form and frequency of an acoustic resonance mode of the combustion chamber volume. The most common mode in naturally occurring instability, and also the most destructive, is the first tangential mode, with acoustic gas oscillations oriented transversally to the direction of propellant injection. The instability is driven by the coupling between acoustic oscillations and unsteady energy release from combustion. The mechanisms through which injection and combustion firstly respond to the acoustic field, and secondly feed energy back into the acoustic field have not yet been fully characterised. Shear coaxial-type injectors are common in LPREs. Past experimental and numerical research efforts have investigated the interaction between this type of injector and transverse acoustic fields. Some experimental efforts have successfully forced transverse acoustic modes and studied their influence on shear coaxial injection under LPRE-like conditions. Acoustic forcing of coaxially injected LOx/H2 has previously been conducted only at low pressures and injection performance levels. This work addresses the lack of experimental data available for the interaction of shear coaxial injection of LOx/H2 with acoustics under conditions representative of industrial engines. A new experimental rocket combustor, designated 'BKH', was developed for investigating the response of a reacting spray of coaxially injected LOx/H2 to an acoustic field. For characterising the response, simultaneous high-speed recordings of both backlit shadowgraph and hydroxyl radical (OH*) chemiluminescence imaging have been captured through optical access windows. The operating conditions of BKH extend to conditions more representative of actual LPREs than has previously been achieved with LOx/H2 in studies of flame-acoustic interaction. BKH was run at pressures of 40 or 60 bar, which correspond to subcritical and supercritical thermo-physical regimes for oxygen. Hydrogen injection temperature was ambient, around 290 K, or cryogenic, around 50 K. An array of multiple injectors was used to better represent real engines. A system for modulating the nozzle exhaust flow was used to induce acoustic perturbations inside the combustion chamber. Two types of perturbation were applied to the near-injection region; oscillating acoustic pressure, and oscillating transverse acoustic velocity. BKH was used to investigate how subcritical or supercritical pressure level and ambient or cryogenic hydrogen injection temperature influence the interaction of acoustic pressure or velocity with injection and combustion processes. Shadowgraph imaging reveals up to 70% reduction in the length of the oxygen jet when subjected to acoustic velocity of amplitude approaching that of the hydrogen injection velocity. Furthermore, the mode of jet breakup changes from its natural growth-and-detachment behaviour to a 'transverse stripping' mechanism. OH* imaging reveals a corresponding decrease in the extent of the flame, and increase in emission intensity. When subjected to acoustic pressure, OH* emission from the flame was observed to fluctuate in phase with pressure. Thus, responses to both acoustic pressure and velocity have been observed in BKH, which together may form the basis of a coupling mechanism for driving natural combustion instability in LPREs.
Author: Leon M. Wenzel
Publisher:
ISBN:
Category : Liquid oxygen
Languages : en
Pages : 20
Get Book Here
Book Description
Author: Terracciano Andrea
Publisher: LAP Lambert Academic Publishing
ISBN: 9783659639166
Category :
Languages : en
Pages : 204
Get Book Here
Book Description
This experimental work regards the studies of the high frequency combustion instabilities inside the DVRC (Discretely Variable Resonance Combustor), a liquid rocket engine, developed by the Purdue University at M. J. Zucrow Laboratories, on behalf of Nasa Marshall Space Flight Center. The research revealed that, given these specific flow conditions, combustion instability occurs inside the system during hot fire tests. The most important experimental result of the study showed the oxidizer manifold acting as a damper of the pressure oscillations coming from the combustion chamber and how this can represent an advantage in terms of reduced mechanical loads at the interface with the rest of the feed system. The LEE code based on the linearized Euler equations detected both the combustion instability inside the DVRC and confirmed the positive role of the oxidizer manifold. The best agreement with the experimental results has been observed considering heat addition at the plane of propellants injection into the combustion chamber, showing it is reasonable to assume combustion occurs mainly in proximity of that plane, as the previous works about CVRC and CFD results had already shown.
Author: Y. M. Kim
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: Luigi Crocco
Publisher:
ISBN:
Category : Combustion
Languages : en
Pages : 216
Get Book Here
Book Description
The report presents a theoretical analysis of combustion instability in liquid rocket motors.
Author: Dieter K. Huzel
Publisher: AIAA
ISBN: 9781600864001
Category : Liquid propellant rocket engines
Languages : en
Pages : 452
Get Book Here
Book Description
